CN104590591B - One is novel arrests and retaining mechanism in-orbit - Google Patents

Abstract

The invention provides a new type of on-orbit capture and locking mechanism, which can effectively capture and lock space objects through the capture phase, axis rotation correction phase, locking phase and release separation phase, especially Solve the angular tolerance of the space vehicle's rotation around the axis, and finally ensure the rapid capture and locking of the space target vehicle, which is conducive to improving the level of my country's on-orbit service technology.

Description

A New Type of On-orbit Capture and Locking Mechanism

technical field

The invention belongs to the field of on-orbit capture of space targets, and relates to the design of an on-orbit capture mechanism for a target aircraft, especially the control of the rotation tolerance around the axis when the target aircraft is captured and pulled closer. It can effectively solve the problem, and finally realize the capture and locking of the target aircraft.

Background technique

Space vehicles play an important role in my country's national economy and national defense industry, and are one of the main means for my country to obtain space information. With the rapid development of my country's space science and technology, some key technologies have reached or approached the advanced level of foreign countries. Aircraft in-orbit service technology has a strong military background, which can provide fast and efficient logistics support for future space militarization, and can directly capture and attack targets, thereby greatly improving space anti-war capabilities.

At present, in my country's aircraft on-orbit service technology system, the processing of space target aircraft on-orbit capture technology is not perfect, and the angle tolerance of the rotation around the axis during the capture process cannot be well controlled. The tight process cannot be handled quickly and effectively, which will affect the function and efficiency of the on-orbit capture mechanism for space targets, and cannot guarantee the function of the aircraft.

Contents of the invention

The purpose of the present invention is to provide a new set of on-orbit capture and locking mechanism to solve the problem of angular tolerance of the space vehicle rotating around the axis.

The present invention adopts the following methods to achieve the above object:

A new type of on-rail capture and locking mechanism, including a base-main bracket 1, a flexible shaft 2, a rotating motor assembly 3, a base-4, a transmission assembly-5, a sleeve assembly 6, a rotating assembly-7, a base Seat Two 8, Automatic Alignment Rod 9, Preload Stop Buckle Assembly 10, Spring Loaded Probe Assembly 11, Rotation Assembly Two 12, Screw Assembly 13, Transmission Assembly Two 14, Locking Motor Assembly 15, Locking Motor Bracket 16, Wire Bar 17, base-auxiliary bracket 18, main motor 19, transmission system 20, screw bearing housing 21, connecting seat 22, auxiliary shaft 23, transmission device bearing 24, transmission device bearing housing 25, transmission device base 26, correction Motor 27, rotating motor coupling 28, rotating motor connecting shaft 29, gear one 30, gear two 31, rotating sleeve 32, rotating sleeve bearing 33, rotating sleeve bearing seat 34, hard docking probe 35, spring 36, End cover 37, preload stop buckle 38, preload stop buckle base 39, lock motor 40, lock motor coupling 41, lock motor connecting shaft 42, gear three 43, gear four 44, lock Sleeve assembly 45, locking lead screw 46, locking screw rod 47, locking sleeve bearing 48, locking sleeve bearing seat 49; take the base-main support 1 as a benchmark, install the transmission system 20, the main motor in sequence 19. Lead screw bearing housing 21, transmission bearing 24, lead screw 17, auxiliary shaft 23, connecting seat 22 and flexible shaft 2; based on base 2 8, install the automatic alignment rod 9, spring-loaded probe assembly 11, Preloading stop buckle 10, locking motor bracket 16, locking motor assembly 15, transmission assembly 2 14, screw assembly 13 and rotating assembly 2 12; wherein base-main bracket 1, lead screw 17 and base-1 are 4 phases Matching, used to fix the position of the base one and ensure the smooth transmission of power; the flexible shaft 2 and the base one 4 cooperate to capture the space on the track; the rotating motor assembly 3, the rotating assembly one 7, the sleeve Component 6, base 2 8, automatic alignment rod 9, preloaded stop buckle component 10 and spring-loaded probe component 11 cooperate to correct the attitude of the space target aircraft; base 2 8, rotating component 2 12, Screw assembly 13, transmission assembly 2 14, locking motor assembly 15 and locking motor support 16 cooperate to be used for locking the space object aircraft;

The rotating motor assembly 3 is mainly composed of a correcting motor 27, a rotating motor coupling 28 and corresponding keys. Under the rotation of the correcting motor 27, the rotating motion of the moving motor is transmitted to the transmission assembly through the rotating motor coupling 28 ;

The transmission system 20 includes gears, shafts, flat keys and mounting plates;

The first transmission assembly 5 and the second transmission assembly 14 are mainly composed of a rotating motor coupling 28 and corresponding keys, a rotating motor connecting shaft 29, and a locking motor connecting shaft 43, mainly to transmit the rotational motion of the motor to the gear one 30 and gear three 43 on;

The first rotating assembly 7 and the second rotating assembly 12 are mainly composed of the first gear 30 and the second gear 31 or the third gear 43 and the fourth gear 44, as well as the corresponding key, the rotating motor coupling 28, and the preloaded stop buckle 38. Under the action of rotating assembly 1 7 and rotating assembly 2 12, driving gear 1 30 meshes with gear 2 31 or gear 3 43 and gear 4 44 to prepare for posture correction or locking;

The sleeve assembly 6 is mainly composed of a rotating sleeve bearing seat 34, a rotating sleeve 32 and a rotating sleeve bearing 33, and mainly acts as an intermediate bridge for power transmission when the target aircraft is corrected for its attitude;

The locking assembly is mainly composed of a locking motor bracket 16, a locking motor 40, a locking motor coupling 41, a locking motor connecting shaft 42, a gear three 43, a gear four 44, a locking screw 46, a locking Screw rod 47 and locking sleeve bearing 48 and locking sleeve bearing seat 49 are formed, and locking motor 40 rotates, drives locking motor coupling 41, locking motor connecting shaft 42 and gear three 43 to rotate together, through gear three 43 and gear four 44 are meshed, and then drive the locking sleeve to rotate, and under the cooperation of the locking screw rod 47, the locking sleeve and the locking screw 46, the screw rod is finally slowly unscrewed;

The spring-loaded probe assembly 11 is mainly composed of a hard docking probe 35, a spring 36, a hollow stepped shaft and a corresponding end cap 37. A spring is installed in the spring-loaded probe, and an end cap 37 is fixed on the periphery. During the process, the target center cone is in contact with the hard docking probe 35, which reduces the impact between the aircraft and eliminates the gap on the one hand, and on the other hand, the spring is compressed to store energy and prepare for the release and separation in the future;

The preloaded stop buckle assembly 10 is mainly composed of a preloaded stop buckle 38, a preloaded stop buckle base 39 and a corresponding torsion spring; the spring loaded probe assembly 11 is mainly composed of a hard docking probe 35, a spring 36 and the corresponding end cap 37, the middle of the spring-loaded probe is equipped with a spring, and the periphery is fixed by the end cap 37; the preloading stopper base 39 is installed and fixed on the base two 8, and the preloading stopper 38 is installed On the preloading stopper base 39, when the hard docking probe 35 is impacted and moves backward, at this time, the hard buttocking probe 35 contacts the preloading stopper 38 and the torsion spring in the preloading stopper 38 is pressed Force, thereby reducing the impact of the two aircraft;

When the target aircraft is within the capture range, the main motor 19 starts, and the rotation of the motor is transmitted to the lead screw 17 through the transmission system 20, and the rotation of the lead screw 17 is transformed by the cooperation of the lead screw 17 and the connecting seat 22. is the linear motion of the connecting seat 22; under the cooperation of the connecting seat 22 and the flexible shaft 2 and the connecting seat 22 and the auxiliary shaft 23, the connecting seat 22 and the flexible shaft 2 are finally realized to perform linear motion together; when the flexible shaft 2 slowly extends to After the locking position of the target center cone and the soft connection are completed, the main motor 19 reverses to pull the flexible shaft 2 and the target aircraft back together; The transmission assembly 5 transmits the rotational movement of the correction motor 27 to the rotation assembly 1 7 and the sleeve assembly 6, and finally the sleeve assembly drives the base 2 8 and the components on it to rotate together, so that the automatic alignment rod 9 is on the roll cover. Within the range; as the target aircraft continues to be drawn closer, the automatic alignment rod 9 contacts with the roll cover to correct the attitude of the target aircraft; at the same time, the spring-loaded probe assembly 11 reduces the impact of the contact between the two aircraft and has a pressurized storage capacity to eliminate the gap After the automatic alignment rod 9 enters the automatic alignment socket, the locking motor assembly 15 starts, and through the cooperation of the transmission assembly two 14, the rotating assembly two 12, the locking sleeve assembly 45, the locking motor assembly 15 and the screw assembly 13, Finally, the screw rod is unscrewed and locked with the automatic alignment socket; when the target aircraft needs to be released and separated, the locking motor assembly 15 is reversed, the screw rod is unscrewed from the automatic alignment socket, and the spring restoring force in the spring-loaded probe assembly Under the action of the target center cone and the contact of the spring-loaded probe assembly 11, the two aircraft are released and separated.

Further, the flexible shaft 2 and the connecting seat 22, the connecting seat and the auxiliary shaft 23 and the lead screw 17 form a complete telescopic mechanism; under the operation of the main motor 19, the rotational motion of the motor is transmitted to the lead screw 17, and the motor is passed through the lead screw 17 to The cooperation between the bar 17 and the connecting seat 22, the connecting seat 22 and the flexible shaft 2, and the connecting seat 22 and the auxiliary shaft 23 finally converts the rotational motion of the main motor 19 into the linear motion of the flexible shaft 2. During this process, the movement of the lead screw 17 The screw pitch is designed to be 2mm, the length is 1800mm, the thickness of the connecting seat 22 is 20mm and the center of the auxiliary shaft 23 is 45mm away from the center of the flexible shaft 2, and the position of 60mm is selected from the leading screw 17.

Further, after the correction motor 27 is started, after the transmission assembly one 5 transmits the selected motion to the base two 8, the terminal rotational angular velocity of the base two 8 should not be greater than rad/s, so as to ensure that there is enough time for locking after correction within the 360° range.

Further, after the locking motor 40 is started, after the rotational movement of the locking motor 40 is transmitted to the locking screw 47, the forward speed of the locking screw 47 is not less than 2mm/s, ensuring that there is enough time for locking; the retracting speed is not less than 4mm/s, used to ensure quick unlock and release.

Further, if the automatic alignment rod 9 is not within the range of the roll cover, the correction motor 27 starts to start, and the rotary motion of the correction motor 27 is transmitted to the first rotating assembly 7 through the transmission assembly 5, and through the engagement of the first gear 30 and the second gear 31, The rotary motion is further transmitted to the sleeve assembly 6, and finally the sleeve assembly drives the base 2 8 and the components on it to rotate together, so that the automatic alignment rod 9 is within the range of the roll cage.

The present invention can effectively capture and lock the space target through the novel on-orbit capture and locking mechanism, especially solve the angle tolerance of the space vehicle rotating around the axis, and finally ensure that the space target vehicle can be quickly grasped. Capture and lock, which is conducive to improving the level of my country's on-orbit service technology.

Description of drawings

Fig. 1 is a schematic diagram of the assembly structure of the present invention;

Figure 2 is a schematic diagram of the positional relationship among the main motor, the transmission device, the flexible shaft and the mounting bracket;

Figure 3 is a schematic diagram of the positional relationship among the automatic alignment rod, the spring-loaded probe, the rotating motor assembly and the calibration assembly;

Figure 4 is a schematic diagram of the structural assembly between the locking assembly, the transmission assembly, the rotating assembly and the screw;

Figure 5 and Figure 6 are schematic diagrams of the process of the flexible shaft capturing the target and actively correcting the attitude;

Fig. 7 and Fig. 8 are schematic diagrams of locking and releasing separation structures of the target aircraft.

detailed description

The structure and function of the novel catching and locking mechanism of the present invention, the catching process, the locking process and the release and separation process will be described in detail below through specific application implementation.

1. The assembly relationship and functions of the main components of the new capture and locking mechanism (Figure 1)

A new type of on-rail capture and locking mechanism, including a base-main bracket 1, a flexible shaft 2, a rotating motor assembly 3, a base-4, a transmission assembly-5, a sleeve assembly 6, a rotating assembly-7, a base Seat Two 8, Automatic Alignment Rod 9, Preload Stop Buckle Assembly 10, Spring Loaded Probe Assembly 11, Rotation Assembly Two 12, Screw Assembly 13, Transmission Assembly Two 14, Locking Motor Assembly 15, Locking Motor Bracket 16, Wire Bar 17, base-auxiliary bracket 18, main motor 19, transmission system 20, screw bearing housing 21, connecting seat 22, auxiliary shaft 23, transmission device bearing 24, transmission device bearing housing 25, transmission device base 26, correction Motor 27, rotating motor coupling 28, rotating motor connecting shaft 29, gear one 30, gear two 31, rotating sleeve 32, rotating sleeve bearing 33, rotating sleeve bearing seat 34, hard docking probe 35, spring 36, End cover 37, preload stop buckle 38, preload stop buckle base 39, lock motor 40, lock motor coupling 41, lock motor connecting shaft 42, gear three 43, gear four 44, lock Sleeve assembly 45, locking lead screw 46, locking screw rod 47, locking sleeve bearing 48, locking sleeve bearing seat 49; take the base-main support 1 as a benchmark, install the transmission system 20, the main motor in sequence 19. Lead screw bearing housing 21, transmission bearing 24, lead screw 17, auxiliary shaft 23, connecting seat 22 and flexible shaft 2; based on base 2 8, install the automatic alignment rod 9, spring-loaded probe assembly 11, Preloading stop buckle 10, locking motor bracket 16, locking motor assembly 15, transmission assembly 2 14, screw assembly 13 and rotating assembly 2 12; wherein base-main bracket 1, lead screw 17 and base-1 are 4 phases Matching, used to fix the position of the base one and ensure the smooth transmission of power; the flexible shaft 2 and the base one 4 cooperate to capture the space on the track; the rotating motor assembly 3, the rotating assembly one 7, the sleeve Component 6, base 2 8, automatic alignment rod 9, preloaded stop buckle component 10 and spring-loaded probe component 11 cooperate to correct the attitude of the space target aircraft; base 2 8, rotating component 2 12, Screw assembly 13, transmission assembly 2 14, locking motor assembly 15 and locking motor support 16 cooperate to be used for locking the space object aircraft;

The rotating motor assembly 3 is mainly composed of a correcting motor 27, a rotating motor coupling 28 and corresponding keys. Under the rotation of the correcting motor 27, the rotating motion of the moving motor is transmitted to the transmission assembly through the rotating motor coupling 28;

Transmission system 20 includes gears, shafts, flat keys and mounting plates;

Transmission assembly one 5 and transmission assembly two 14 are mainly composed of rotating motor coupling 28 and corresponding keys, rotating motor connecting shaft 29, and locking motor connecting shaft 43, mainly to transmit the rotational motion of the motor to gear one 30 and gear Three 43 on;

Rotating assembly one 7 and rotating assembly two 12 are mainly composed of gear one 30 and gear two 31 or gear three 43 and gear four 44, as well as corresponding keys, rotating motor couplings 28, and preloaded stop buckles 38. Under the action of 7 and rotating assembly 2 12, driving gear 1 30 and gear 2 31 or gear 3 43 and gear 4 44 are meshed to prepare for attitude correction or locking;

The sleeve assembly 6 is mainly composed of a rotating sleeve bearing seat 34, a rotating sleeve 32 and a rotating sleeve bearing 33, and mainly plays the role of an intermediate bridge for power transmission when the target aircraft is corrected for its attitude;

The locking assembly mainly consists of a locking motor support 16, a locking motor 40, a locking motor coupling 41, a locking motor connecting shaft 42, a gear three 43, a gear four 44, a locking screw 46, a locking screw 47 and Locking sleeve bearing 48 and locking sleeve bearing seat 49 are formed, and locking motor 40 rotates, drives locking motor coupling 41, locking motor connecting shaft 42 and gear three 43 to rotate together, through gear three 43 and gear Four 44 are meshed, and then the locking sleeve is driven to rotate, and finally the screw is slowly unscrewed under the cooperation of the locking screw 47, the locking sleeve and the locking screw 46;

The spring-loaded probe assembly 11 is mainly composed of a hard docking probe 35, a spring 36, a hollow stepped shaft and a corresponding end cap 37. A spring is installed in the middle of the spring-loaded probe, and an end cap 37 is fixed on the periphery. In the process of approaching the target aircraft , the target center cone is in contact with the hard docking probe 35, on the one hand, it reduces the impact between the aircraft and eliminates the gap, on the other hand, the spring is compressed to store energy and prepare for the release and separation in the future;

The preloaded stop buckle assembly 10 is mainly composed of a preloaded stop buckle 38, a preloaded stop buckle base 39 and corresponding torsion springs; the spring loaded probe assembly 11 is mainly composed of a hard docking probe 35, a spring 36 and corresponding The end cover 37 is made up of, and spring is installed in the middle of spring loaded probe, and end cover 37 is fixed on the periphery; On the stop buckle base 39, when the hard butt joint probe 35 is impacted and moves backward, at this moment, the hard butt joint probe 35 contacts the preload stop buckle 38 and makes the torsion spring in the preload stop buckle 38 stressed, thereby Reduce the impact of the two aircraft.

2. Description of the capture process of the new capture and locking mechanism

The capture process can be divided into two phases: the detection phase and the capture phase.

1) Detection stage

Under the detection of the detection device, if the target aircraft is not within the capture range, the service aircraft continues to adjust the attitude until the target aircraft is within the capture range; if the target aircraft is within the capture range, the main motor 19 is driven to prepare start working.

2) Capture stage

The main motor 19 is started, and the rotational motion of the motor is transmitted to the lead screw 17 through the transmission system 20. The two ends of the lead screw 17 are respectively equipped with transmission device bearings 24 and transmission device bearing seats 25 to position the lead screw; The cooperation of the seat 22 converts the rotary motion of the lead screw 17 into the linear motion of the connecting seat 22; under the cooperation of the connecting seat 22 and the flexible shaft 2 and the connecting seat 22 and the auxiliary shaft 23, the auxiliary shaft 23 is finally realized as the connecting seat 22 The rectilinear motion provides a track, and the connecting seat 22 and the flexible shaft 2 do rectilinear motion together. When the flexible shaft 2 is slowly stretched into the locking position of the target center cone and the flexible connection is completed, the main motor 19 reverses to pull the flexible shaft 2 and the target aircraft back together.

3. Description of the locking process of the new capture and locking mechanism

The locking process can be divided into two stages: axis rotation correction stage and locking stage.

1) Axis rotation correction stage

After the target aircraft is pulled closer, under the detection of the detection device, it is judged whether the automatic alignment rod 9 is within the range of the roll cover of the target aircraft.

If it is within the range, then there is no need to perform rotation correction; if the automatic alignment rod 9 is not within the range of the roll cover, the correction motor 27 starts to start, and the rotational movement of the correction motor 27 is transmitted to the rotation assembly 7 through the transmission assembly one 5. The meshing of gear 1 30 and gear 2 31, the rotation motion is further transmitted to the sleeve assembly 6, and finally the sleeve assembly drives the base 2 8 and the components on it to rotate together, so that the automatic alignment rod 9 is within the range of the roll cover .

2) Locking stage

As the target aircraft continues to be drawn closer, the automatic alignment rod 9 contacts with the roll cover to correct the attitude of the target aircraft; at the same time, the target center cone contacts with the spring-loaded probe assembly 11, on the one hand buffering the impact of the contact between the two aircraft, and on the other hand On the one hand the spring 36 in the spring loaded probe assembly is compressed and stores capacity, eliminates the gap, and prepares for separation release.

After the automatic alignment rod 9 enters the automatic alignment socket, the locking motor 40 starts, and through the cooperation of the transmission assembly 2 14, the rotating assembly 12 and the locking sleeve assembly 45, the locking screw rod will be locked by the action of the locking motor 40. 47 is unscrewed and locked with the automatic alignment socket.

4. Description of the release and separation process of the new capture and locking mechanism

When the target aircraft needs to be released and separated, the locking motor 40 reverses, and the locking screw 47 is unscrewed from the automatic alignment socket. Under the restoring force of the spring 36 in the spring-loaded probe assembly, the target center cone and the spring-loaded probe The contact of the components 11 releases the separation of the two aircraft.

Claims (5)

1. novel arrest in-orbit and retaining mechanism for one kind, it is characterised in that: include pedestal one main support (1), flexible axle (2), rotate Electric machine assembly (3), pedestal one (4), transmission component one (5), sleeve assembly (6), runner assembly one (7), pedestal two (8), automatically Alignment rod (9), preloading detent assembly (10), spring load probe assembly (11), runner assembly two (12), screw arbor assembly (13), transmission component two (14), locking motor assembly (15), locking motor support (16), leading screw (17), pedestal one auxiliary stand (18), mair motor (19), transmission system (20), lead screw shaft bearing (21), connection seat (22), asessory shaft (23), transmission device axle Hold (24), actuator beairng seat (25), actuator base (26), correcting motor (27), rotating machine coupling (28), rotation Rotating motor connecting shaft (29), gear one (30), gear two (31), turnbarrel (32), turnbarrel bearing (33), turnbarrel Bearing block (34), firm docking probe (35), spring (36), end cap (37), preloading detent (38), preloading detent pedestal (39), locking motor (40), locking motor shaft coupling (41), locking motor connecting shaft (42), gear three (43), gear four (44), locking sleeve assembly (45), locking screw (46), tie down screw (47), locking sleeve bearing (48), locking sleeve bearing Seat (49)；On the basis of pedestal one main support (1), transmission system (20), mair motor (19), lead screw shaft bearing are installed successively (21), actuator beairng (24), leading screw (17), asessory shaft (23), connection seat (22) and flexible axle (2)；With pedestal two (8) as base Standard, installation automatic aligning bar (9) successively, spring loading probe assembly (11), preloading detent assembly (10), locking motor prop up Frame (16), locking motor assembly (15), transmission component two (14), screw arbor assembly (13) and runner assembly two (12)；Wherein pedestal One main support (1), leading screw (17) and pedestal one (4) match, for the position of fixed pedestal one and the smooth biography of guarantee power Pass；Flexible axle (2) and pedestal one (4) match, for arresting space in-orbit；Electric rotating machine assembly (3), runner assembly one (7), sleeve assembly (6), pedestal two (8), automatic aligning bar (9), preloading detent assembly (10) and spring load probe group Part (11) matches, for extraterrestrial target aircraft carries out the correction of attitude；Pedestal two (8), runner assembly two (12), screw rod Assembly (13), transmission component two (14), locking motor assembly (15) and locking motor support (16) match, for by space mesh Mark aircraft locking；

Described electric rotating machine assembly (3) is mainly made up of correcting motor (27), rotating machine coupling (28) and corresponding key, Under the rotation of correcting motor (27), by rotating machine coupling (28), the rotary motion of motion motor is transferred to transmission group Part；

Described transmission system (20) includes gear, axle, flat key and installing plate；Described transmission component one (5), transmission component two (14) main by rotating machine coupling (28) and corresponding key and electric rotating machine connecting shaft (29), locking motor connecting shaft (42) composition, is mainly transferred to the rotary motion of motor on gear one (30) and gear three (43)；

Described runner assembly one (7), runner assembly two (12) are main by gear one (30) and gear two (31) or gear three (43) and gear four (44) and corresponding key and rotating machine coupling (28), preload detent (38) composition, rotating Under the effect of assembly one (7) and runner assembly two (12), drive gear one (30) and gear two (31) or gear three (43) and Gear four (44) is meshed, for correcting attitude or locking ready；

Described sleeve assembly (6) is main by turnbarrel bearing block (34), turnbarrel (32) and turnbarrel bearing (33) group Become, when target aircraft is carried out attitude updating, act primarily as the intermediate axle beam effect of transmission power；

Described locking motor support (16), locking motor (40), locking motor shaft coupling (41), locking motor connecting shaft (42), gear three (43), gear four (44), locking screw (46), tie down screw (47) and locking sleeve bearing (48) and lock Tight sleeve bearing seat (49) composition latch assembly, locking motor (40) rotates, and drives locking motor shaft coupling (41), locking motor Connecting shaft (42) rotates together with gear three (43), is meshed by gear three (43) and gear four (44), and then drives locking Sleeve rotating, at tie down screw (47) with under the cooperation of locking sleeve and locking screw (46), screw rod screws out slowly the most at last；

Described spring loads probe assembly (11) mainly by firm docking probe (35), spring (36), hollow multidiameter and corresponding End cap (37) composition, spring load probe in spring is installed, be with outward end cap (37) fix, target aircraft is close During, target's center's cone contacts with firm docking probe (35), on the one hand reduces the impact between aircraft and eliminates gap, On the other hand spring pressurized, stores energy, separates for later release and prepares；

Described preloading detent assembly (10) is mainly by preloading detent (38), preloading detent pedestal (39) and phase The torsion spring composition answered；Described spring loads probe assembly (11) mainly by firm docking probe (35), spring (36) and accordingly End cap (37) forms, and spring loads the centre of probe and is provided with spring, is with outward end cap (37) and fixes；Preload detent pedestal (39) it is mounted and fixed on pedestal two (8), preloads detent (38) and be arranged in preloading detent pedestal (39), firmly Docking probe (35) is by impact rearward movement, and now, firm docking probe (35) contacts with preloading detent (38) and makes pre- Load the torsion spring stress in detent (38), thus reduce the impact of two aircraft；

When target aircraft is within the scope of arresting, mair motor (19) starts, through transmission system (20) by the rotation of motor Motion is transferred on leading screw (17), by leading screw (17) and the cooperation being connected seat (22), by the convert rotational motion of leading screw (17) For connecting the linear motion of seat (22)；Connect seat (22) with flexible axle (2) and be connected seat (22) with under the cooperation of asessory shaft (23), Final realization connects seat (22) and moves along a straight line together with flexible axle (2)；When flexible axle (2) slowly stretches to the locking of target's center's cone Position after completing to be flexible coupling, mair motor (19) inverts, and is retracted by flexible axle (2) together with target aircraft；If automatic aligning Bar (9) is not within the scope of anti-roll cover, and correcting motor (27) starts to start, through transmission component one (5) by correcting motor (27) rotary motion is transferred on runner assembly one (7) and sleeve assembly (6), final sleeve assembly band moving base two (8) and Assembly above it rotates together so that automatic aligning bar (9) is within the scope of anti-roll cover；Along with target aircraft continues Furthering, automatic aligning bar (9) contacts with anti-roll cover, and target aircraft is carried out attitude updating；Meanwhile, spring loads probe assembly (11) alleviate impact the pressurized storage capacity of two aircraft contacts, eliminate gap；When automatic aligning bar (9) enter to the most right After neat socket, locking motor assembly (15) starts, through transmission component two (14), runner assembly two (12), locking sleeve group Part (45) and locking motor assembly (15) and the cooperation of screw arbor assembly (13), the most at last screw rod screw out and with automatic aligning socket Lock；When target aircraft needs release to separate, locking motor assembly (15) inverts, by screw rod from automatic aligning socket Middle back-out, under the effect of the spring restoring force in spring loads probe assembly, loads probe by target's center's cone with spring Two aircraft releases are separated by the contact of assembly (11).

One the most according to claim 1 is novel arrests and retaining mechanism in-orbit, it is characterised in that: flexible axle (2) be connected Seat (22), connect seat and asessory shaft (23) and leading screw (17) coordinate formed complete telescoping mechanism；At mair motor (19) Under work, the rotary motion of motor is transferred to leading screw (17), through leading screw (17) be connected seat (22), connect seat (22) with soft Axle (2) and connect seat (22) and the coordinating of asessory shaft (23), the convert rotational motion of mair motor (19) is flexible axle (2) the most at last Linear motion, during this, the pitch of leading screw (17) be designed as 2mm, a length of 1800mm, connect seat (22) thickness be 20mm and asessory shaft (23) centre-to-centre spacing flexible axle (2) center 45mm, the position away from leading screw (17) 60mm selects.

One the most according to claim 1 is novel arrests and retaining mechanism in-orbit, it is characterised in that: in correcting motor (27) Starting, after selection campaign is transferred to pedestal two (8) by transmission component one (5), the end angular velocity of rotation of pedestal two (8) should It is not more thanRad/s, thus ensure enough time can be had to lock after correcting in the range of 360 °.

One the most according to claim 1 is novel arrests and retaining mechanism in-orbit, it is characterised in that: locking motor (40) opens After Dong, after locking motor (40) rotary motion is transferred to tie down screw (47), the pace of tie down screw (47) is not less than 2mm/s, it is ensured that have enough time to lock；The speed regained, not less than 4mm/s, is used for guaranteeing quick release release.

One the most according to claim 1 is novel arrests and retaining mechanism in-orbit, it is characterised in that: if automatic aligning bar (9) not within the scope of anti-roll cover, correcting motor (27) starts to start, through transmission component one (5) by correcting motor (27) Rotary motion be transferred to runner assembly one (7), by gear one (30) and the engagement of gear two (31), rotary motion enters one Step is transferred on sleeve assembly (6), and final sleeve assembly band moving base two (8) rotates together with the assembly above it so that from Dynamic alignment rod (9) is within the scope of anti-roll cover.